# Boeing Special Attention Service Bulletin 767-57-0121: U.S. DOT/FAA - Service Bulletin

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- Document: [Boeing Special Attention Service Bulletin 767-57-0121](https://openairdocs.org/service-documents/boeing/sb-767-57-0121.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin
- Pages: 68
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### Page 1

Commercial 
Airplanes
767
Service Bulletin
SPECIAL ATTENTION
Number: 767-57-0121
Original Issue: October 07, 2010
ATA System: 5700
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge Fluid Drainage
Path Change
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2010 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 7
A. Effectivity ................................................ 7
1. Airplanes ............................................. 7
2. Spares Affected ........................................ 1 3
B. Concurrent Requirements ...................................... 1 3
C. Reason ................................................ 1 3
D. Description .............................................. 1 3
E. Compliance .............................................. 1 3
F. Approval ............................................... 1 4
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 5
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 1 5
1. Existing Data .......................................... 1 5
2. Data supplied with this Service Bulletin ............................ 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 6
K. Publications Affected ........................................ 1 6
L. Interchangeability and Intermixability of Parts ........................... 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary For Each Airplane ................................. 1 8
1. Kits/Parts ............................................ 1 8
2. Parts and Materials Supplied by the Operator ........................ 1 9
3. Parts Modified and Reidentified ................................ 2 0
4. Parts Removed and Not Replaced .............................. 2 0
D. Parts Necessary to Change Spares ................................. 2 0
E. Special Tooling - Price and Availability ............................... 2 0
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 1
A. GENERAL INFORMATION ..................................... 2 1
B. WORK INSTRUCTIONS ....................................... 2 2
FIGURE 1: LEFT WING SKIN PANEL 521AB CHANGE ......................... 2 5
FIGURE 2: RIGHT WING SKIN PANEL 621AB CHANGE ........................ 2 7
FIGURE 3: LEFT WING SKIN PANEL 521EB CHANGE ......................... 2 9
FIGURE 4: RIGHT WING SKIN PANEL 621EB CHANGE ........................ 3 3
FIGURE 5: LEFT WING SEAL DOOR CHANGE AT OSS 424.097 ................... 3 7
FIGURE 6: RIGHT WING SEAL DOOR CHANGE AT OSS 424.097 ................... 4 0
FIGURE 7: LEFT WING RIB CHANGE AT OSS 464.475 ......................... 4 3
FIGURE 8: RIGHT WING RIB CHANGE AT OSS 464.475 ........................ 4 7
FIGURE 9: LEFT WING LEADING EDGE SEALING ........................... 5 1
FIGURE 10: RIGHT WING LEADING EDGE SEALING .......................... 5 5
FIGURE 11: LEFT WING RIB SEALING AT OSS 464.475 ......................... 5 9
FIGURE 12: RIGHT WING RIB SEALING AT OSS 464.475 ........................ 6 4
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Commercial 
Airplanes
767
Service Bulletin
SPECIAL ATTENTION
SummaryNumber: 767-57-0121Original Issue: October 07, 2010
ATA System: 5700
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge Fluid Drainage
Path Change
BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions to modify the fluid drain path in the wing leading edge area, forward of
the wing front spar. If this service bulletin is not incorporated, flammable fluids accumulating in the wing leading
edge may drain inboard and onto the engine exhaust nozzle, which could result in a fire.
Boeing has received a report of leaking fuel from the wing leading edge area at the inboard end of the number
5 leading edge slat of a 737 airplane. The leak was discovered during a post flight inspection with a fuel quantity
of over 2500 lbs. Subsequent investigation found that the leak occurred in an area of the front spar that does
not have a proper drain path. This led to the fuel draining onto the engine exhaust nozzle. The leak appears to
have been caused by a loose retaining nut of the slat track down stop and is the subject of Boeing Service Letter
737-SL-57-084.
Accomplishment of this service bulletin will make sure that there is a drain path to safely direct all fluid leakages
from the wing leading edge away from the engine exhaust area.
Boeing Service Related Problem (SRP) 767-SRP-57-0213 is related to this service bulletin.
ACTION (PRR B12901-92S)
Get access to the leading edge of the wing by removing access panels. Repair two access panels on each wing.
Install parts in rib and slat door. Apply sealant to create a fuel vapor barrier and a drain path. Close access.
EFFECTIVITY
767-200, -300, -300F, -400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
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Boeing recommends that the change given in this service bulletin be done within 60 months after the original
issue date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of November 15, 2007. Please refer to
Paragraph 2.B., Industry Support Information.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
19.7522.00All Airplanes
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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Commercial 
Airplanes
767
Service Bulletin
SPECIAL ATTENTION
Number: 767-57-0121
Original Issue: October 07, 2010
ATA System: 5700
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge Fluid Drainage
Path Change
BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR B12901-92S for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
767 Airplanes with line number 1-992.-1
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
1VA001 - VA020
1VA301 - VA315
1VA501 - VA530
1VA701 - VA719
1VA801 - VA810
1VB001 - VB002
1VB051 - VB055
1VB101 - VB125
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GroupVariable Number
1VB201 - VB202
1VB251 - VB253
1VB281 - VB284
1VB301 - VB302
1VB321 - VB332
1VB371 - VB373
1VB401
1VB441 - VB444
1VE001 - VE003
1VE021 - VE023
1VE041 - VE043
1VE061 - VE069
1VE083 - VE086
1VE101 - VE104
1VE116 - VE118
1VE121 - VE126
1VE141 - VE152
1VE171 - VE172
1VF001 - VF002
1VF041 - VF042
1VF051
1VF061 - VF062
1VF071 - VF072
1VF091 - VF093
1VF101 - VF102
1VF161 - VF162
1VF171 - VF172
1VF180 - VF184
1VF251
1VK001 - VK016
1VK021 - VK022
1VK031 - VK056
1VK081 - VK113
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GroupVariable Number
1VK131 - VK133
1VK141 - VK148
1VK161 - VK164
1VK171
1VK181
1VK186
1VL001 - VL006
1VL011
1VL701 - VL703
1VL751 - VL755
1VL806 - VL807
1VL871 - VL873
1VL891 - VL900
1VL911 - VL914
1VL931 - VL932
1VL941
1VN001 - VN041
1VN051 - VN064
1VN081 - VN099
1VN111 - VN127
1VN130 - VN137
1VN151 - VN158
1VN163 - VN168
1VN171 - VN174
1VN191 - VN198
1VN211 - VN212
1VN221 - VN225
1VN231 - VN234
1VN241 - VN243
1VN251 - VN276
1VN291 - VN293
1VN301 - VN314
1VN371 - VN372
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GroupVariable Number
1VN376
1VN381 - VN388
1VN421 - VN427
1VN436
1VN471 - VN472
1VN491 - VN513
1VN531 - VN532
1VN536 - VN537
1VN541 - VN542
1VN546 - VN547
1VN551
1VN556 - VN557
1VN561 - VN562
1VN631 - VN638
1VN651 - VN658
1VN671 - VN672
1VN676
1VN681 - VN691
1VN731 - VN732
1VN751 - VN753
1VN791 - VN792
1VN811 - VN813
1VN921 - VN922
1VN931 - VN936
1VN951 - VN953
1VN966 - VN972
1VQ001 - VQ021
1VQ071 - VQ086
1VQ111
1VR051 - VR060
1VR081
1VR084
1VR086 - VR089
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GroupVariable Number
1VR106 - VR109
1VR201 - VR211
1VR251
1VR256 - VR260
1VR266 - VR272
1VR401
1VR421 - VR423
1VR426
1VR441
1VR461
1VR471 - VR472
1VS051 - VS056
1VS061
1VS066 - VS070
1VS073 - VS078
1VS091 - VS104
1VS111 - VS113
1VS131 - VS133
1VS136 - VS137
1VS176 - VS177
1VS186 - VS187
1VS196 - VS203
1VS206 - VS208
1VS211
1VS216 - VS217
1VS231
1VS246 - VS248
1VS261 - VS263
1VS266 - VS274
1VS291 - VS293
1VS301 - VS303
1VS306 - VS311
1VS316
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GroupVariable Number
1VS321 - VS324
1VS331 - VS333
1VS336 - VS337
1VS366 - VS367
1VS381 - VS382
1VS391 - VS392
1VS401
1VS426 - VS428
1VS466 - VS472
1VS486
1VS496 - VS497
1VS506 - VS507
1VS526
1VS546 - VS549
1VS701 - VS736
1VS751 - VS759
1VS821 - VS825
1VS841 - VS844
1VS861
1VS881 - VS883
1VS891
1VS896
1VS901 - VS912
1VS916
1VS921 - VS925
1VS931 - VS933
1VS941
1VT501
1VT511 - VT513
1VT521 - VT523
1VT531 - VT533
1VT541 - VT543
1VV001
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GroupVariable Number
1VW701 - VW721
1VW851
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to modify the fluid drain path in the wing leading edge area,
forward of the wing front spar. If this service bulletin is not incorporated, flammable fluids accumulating
in the wing leading edge may drain inboard and onto the engine exhaust nozzle, which could result in
a fire.
Boeing has received a report of leaking fuel from the wing leading edge area at the inboard end of the
number 5 leading edge slat of a 737 airplane. The leak was discovered during a post flight inspection
with a fuel quantity of over 2500 lbs. Subsequent investigation found that the leak occurred in an area
of the front spar that does not have a proper drain path. This led to the fuel draining onto the engine
exhaust nozzle. The leak appears to have been caused by a loose retaining nut of the slat track down
stop and is the subject of Boeing Service Letter 737-SL-57-084.
Accomplishment of this service bulletin will make sure that there is a drain path to safely direct all fluid
leakages from the wing leading edge away from the engine exhaust area.
Boeing Service Related Problem (SRP) 767-SRP-57-0213 is related to this service bulletin.
D. Description
Get access to the leading edge of the wing by removing access panels. Repair two access panels on
each wing. Install parts in rib and slat door. Apply sealant to create a fuel vapor barrier and a drain
path. Close access.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
533, 633767-200, 767-300, 767-300F,
767-400ER
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
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Boeing recommends that the change given in this service bulletin be done within 60 months after the
original issue date of this service bulletin.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Elapsed HoursTask HoursNumber of PersonsTask
1.252.502Open Access
0.750.751Part 1: FIGURE 1
0.750.751Part 1: FIGURE 2
2.002.001Part 1: FIGURE 3
2.002.001Part 1: FIGURE 4
0.500.501Part 1: FIGURE 5
0.500.501Part 1: FIGURE 6
1.501.501Part 2: FIGURE 7
1.501.501Part 2: FIGURE 8
1.001.001Part 3: FIGURE 9
1.001.001Part 3: FIGURE 10
3.003.001Part 3: FIGURE 11
3.003.001Part 3: FIGURE 12
1.002.002Close Access
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Elapsed HoursTask HoursNumber of PersonsTask
19.7522.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+ 1682.2+ 1.5All
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Engineering Change Memo PRR B12901-92S
b. Boeing Service Letter 737-SL-57-084
c. Boeing Service Related Problem (SRP) 767-SRP-57-0213
d. Standard Overhaul Practices Manual (SOPM) 20-43-03, 20-44-04, 20-50-10, 20-50-12,
20-50-19
e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19
f. 767 Aircraft Maintenance Manual (AMM) 06-44-00, 27-81-00, 51-31-01, 78-31-00
g. 767-200 Structural Repair Manual (SRM) 51-70-08
h. 767-200SF Structural Repair Manual (SRM) 51-70-08
i. 767-300 Structural Repair Manual (SRM) 51-70-08
j. 767-300BCF Structural Repair Manual (SRM) 51-70-08
k. 767-300F Structural Repair Manual (SRM) 51-70-08
l. 767-400 Aircraft Maintenance Manual (AMM) 06-44-00, 27-81-00, 51-31-01, 78-31-00
m. 767-400 Structural Repair Manual (SRM) 51-70-08
2. Data supplied with this Service Bulletin
None.
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3. Installation Drawings Used in the Preparation of this Service Bulletin
None.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kit shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are
encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The
kit is subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
$651.002871October 15,
2010
TOP KIT - 767 Wing
Leading Edge Drainage
Redesign
015T1837-1
25November 5,
2010
25November 30,
2010
25December 17,
2010
25January 21,
2011
25February 11,
2011
25March 4, 2011
B. Industry Support Information
Boeing warranty remedies are available for 767 airplanes in warranty as of November 15, 2007. For
task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing
Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be
supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service
bulletin number and reference the airplane variable numbers in your purchase order.
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C. Parts Necessary For Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for
each installation figure shown in the table below.
Figure Kit
654321Top Kit
111111015T1837-1
Figure Kit
87Top Kit
11015T1837-1
ALL
KIT 015T1837-1
NOTES
Existing Part
NumberName
Figure
New Part Number
654321
QTY
DETAIL, TAB11114T2605-19
DETAIL, PLATE11114T2605-21
INSERT, DRAIN
HOLE
1169B12065-1
RIVET22BACR15CE5AD4
RIVET33BACR15CE5AD5
ALL
KIT 015T1837-1
NOTES
Existing Part
NumberName
Figure
New Part Number
87
QTY
DETAIL, PLUG
OUTER
22114T2605-15
DETAIL, PLUG IN-
NER
11114T2605-17
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ALL
KIT 015T1837-1
NOTES
Existing Part
NumberName
Figure
New Part Number
87
QTY
BOLT11BACB30NR4K7
BOLT33BACB30VT6K5
COLLAR33BACC30BL6
NUT11BACN10YR4CD
SEAL, RING33BACS11BD8
SEAL11BACS45B4
WASHER11BACW10BN4AC
RING, RETAIN-
ING, EXT
11MS16624-2175
WASHER11NAS1149D0463J
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number /
Specification
(a)Sealant-BMS5-45
(a)Primer-BMS10-79, TYPE
III
(a)Enamel-BMS10-60, TYPE
II, BAC707 GRAY
GLOSS
(a)Hole Filling Compound-BMS5-16
(a)Leveling Compound-BMS5-125 TYPE
III
(a)Sealant-BMS5-142
Chemical Conversion Coating-Refer to SOPM 20-
43-03
Parting Agent-Refer to SOPM 20-
50-19
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
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3. Parts Modified and Reidentified
NotesNew Part NumberNameQTYExisting Part
Number
(a) (b) (c) (d)114T2400-( )Skin Panel, Outboard,
Lower Leading Edge,
Outboard
1114T2400-( )
(521EB) (521EB)
SB 767-57-0121
(a) (b) (c) (d)114T2400-( )Skin Panel, Outboard,
Lower Leading Edge,
Outboard
1114T2400-( )
(621EB) (621EB)
SB 767-57-0121
(a) Make the change in accordance with this service bulletin.
(b) There is no equivalent Boeing part number for the changed part. Identify on the part that
the change done in accordance with this service bulletin was made.
(c) This is the part number after the change is done in accordance with this service bulletin.
(d) This part is not used in production.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 21

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets are in Structural Repair Manual (SRM)
Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
5. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51. Alternate fasteners are listed in SRM Chapter 51 and Boeing
Drawing 012W6100.
6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
7. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51.
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### Page 22

8. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
9. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
10. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
11. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
The removed part can be discarded if a new or serviceable part is installed.
12. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is
permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'
(dash) part number. Boeing Drawing 005W0900 contains more data.
B. WORK INSTRUCTIONS
OPEN ACCESS
1. Deactivate the thrust reverser for ground maintenance. Refer to 767 AMM 78-31-00 or 767-400
AMM 78-31-00 as an accepted procedure, as applicable.
2. Extend the leading edge slats. Refer to 767 AMM 27-81-00 or 767-400 AMM 27-81-00 as an
accepted procedure, as applicable.
3. Remove the panels listed below. Refer to 767 AMM 06-44-00 or 767-400 AMM 06-44-00 as an
accepted procedure, as applicable.
Right WingLeft Wing
621AB - Skin Panel, Outboard, Lower Leading Edge521AB - Skin Panel, Outboard, Lower Leading Edge
621AMB - Pressure Relief Panel, Lower Leading Edge521AMB - Pressure Relief Panel, Lower Leading Edge
621BB - Skin Panel, Outboard, Lower Leading Edge521BB - Skin Panel, Outboard, Lower Leading Edge
621ANB - Pressure Relief Panel, Lower Leading Edge521ANB - Pressure Relief Panel, Lower Leading Edge
621EB - Skin Panel, Outboard, Lower Leading Edge,
Outboard
521EB - Skin Panel, Outboard, Lower Leading Edge,
Outboard
4. Remove the seal door at Outboard Slat Station (OSS) 424.097 of the left and right wing. Refer to
767 AMM 57-41-56 or 767-400 AMM 57-41-56 as an accepted procedure, as applicable.
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### Page 23

Part 1 - Lower Wing Skin Change
1. Change the leading edge lower wing skin panels below in accordance with the applicable figures
below:
Right WingLeft Wing
FIGURE 2621ABFIGURE 1521AB
FIGURE 4621EBFIGURE 3521EB
2. Change the seal door at OSS 424.097 in accordance with the figures below:
Right WingLeft Wing
FIGURE 6FIGURE 5
Part 2 - Rib Change
1. Change the ribs at OSS 464.475 in accordance with the figures below:
Right WingLeft Wing
FIGURE 8FIGURE 7
Part 3 - Drain Path Sealing
1. Apply sealant, hole filling compound and leveling compound in the leading edge in accordance
with the figures below:
Right WingLeft Wing
FIGURE 10FIGURE 9
2. Apply sealant to the ribs at OSS 464.475 in accordance with the figures below:
Right WingLeft Wing
FIGURE 12FIGURE 11
CLOSE ACCESS
1. Install the seal door at OSS 424.097 of the left and right wing. Refer to 767 AMM 57-41-56 or
767-400 AMM 57-41-56 as an accepted procedure, as applicable.
2. Install the panels listed below. Refer to 767 AMM 06-44-00 or 767-400 AMM 06-44-00 as an
accepted procedure, as applicable.
Right WingLeft Wing
621AB - Skin Panel, Outboard, Lower Leading Edge521AB - Skin Panel, Outboard, Lower Leading Edge
621AMB - Pressure Relief Panel, Lower Leading Edge521AMB - Pressure Relief Panel, Lower Leading Edge
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### Page 24

Right WingLeft Wing
621BB - Skin Panel, Outboard, Lower Leading Edge521BB - Skin Panel, Outboard, Lower Leading Edge
621ANB - Pressure Relief Panel, Lower Leading Edge521ANB - Pressure Relief Panel, Lower Leading Edge
3. Retract the leading edge slats. Refer to 767 AMM 27-81-00 or 767-400 AMM 27-81-00 as an
accepted procedure, as applicable.
4. Activate the thrust reversers. Refer to 767 AMM 78-31-00 or 767-400 AMM 78-31-00 as an accepted
procedure, as applicable.
5. Put the airplane back to serviceable condition.
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BOEING SERVICE BULLETIN 767-57-0121
3 LOCATIONS
0.91  - 0.24  0.39
0.24  B
1.21
B
†  PLATE
(3)4)  5
1.66
1.54
1.02  INSERT
0.90
INBD  INBD  1996543
A-A  B-B
FIGURE 1: LEFT WING SKIN PANEL 521AB CHANGE
(SHEET 1 OF 2)
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### Page 26

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
as shown.1114T2605-21DETAIL, PLATEPut / Hold1
as shown.3-HoleLocate2
through plate and
panel. Final hole
size is 0.159 - 0.167
inch. Countersink is
100 degrees.
3-HoleDrill
1114T2605-21DETAIL, PLATERemove / Keep3
and deburr.3-HoleClean
Fay surface seal en-
tire surface of plate.
Refer to SOPM 20-
50-19 as an accept-
ed procedure.
-BMS5-45SealantApply4
1114T2605-21DETAIL, PLATEInstall (New)5
3BACR15CE5AD5RIVETInstall (New)
Apply fillet seal
around plate. Refer
to SOPM 20-50-19
as an accepted pro-
cedure.
-BMS5-45SealantApply
Fill entire hole with
sealant. Refer to 767
AMM 51-31-01 or
767-400 AMM 51-
31-01, as applicable,
as an accepted pro-
cedure for aerody-
namic smoothness
information.
-BMS5-45SealantApply6
FIGURE 1: LEFT WING SKIN PANEL 521AB CHANGE
(SHEET 2 OF 2)
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
3 LOCATIONS
FWD
0.39  0.24  0.91
0.24
1.21
PLATE
1.66
2)  1.54
INSERT  • 1.02
0.90
IBD  INBD  1997889
A-A  B-B
FIGURE 2: RIGHT WING SKIN PANEL 621AB CHANGE
(SHEET 1 OF 2)
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### Page 28

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
as shown.1114T2605-21DETAIL, PLATEPut / Hold1
as shown.3-HoleLocate2
through plate and
panel. Final hole
size is 0.159 - 0.167
inch. Countersink is
100 degrees.
3-HoleDrill
1114T2605-21DETAIL, PLATERemove / Keep3
and deburr.3-HoleClean
Fay surface seal en-
tire surface of plate.
Refer to SOPM 20-
50-19 as an accept-
ed procedure.
-BMS5-45SealantApply4
1114T2605-21DETAIL, PLATEInstall (New)5
3BACR15CE5AD5RIVETInstall (New)
Apply fillet seal
around plate. Refer
to SOPM 20-50-19
as an accepted pro-
cedure.
-BMS5-45SealantApply
Fill entire hole with
sealant. Refer to 767
AMM 51-31-01 or
767-400 AMM 51-
31-01, as applicable,
as an accepted pro-
cedure for aerody-
namic smoothness
information.
-BMS5-45SealantApply6
FIGURE 2: RIGHT WING SKIN PANEL 621AB CHANGE
(SHEET 2 OF 2)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
- B
2.25
1.75
1.90
1.70
PANEL  6000
2.80
2.60
FWD  2.25
INSERT  1.75
B-B
NBD  1996952
A-A
FIGURE 3: LEFT WING SKIN PANEL 521EB CHANGE
(SHEET 1 OF 4)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
TEDLAR
APPLICATION
EXTRA
REPAIR PLY
ADHESIVE
FILM
5 ORIGINAL
PLIES
EXTRA REPAIR
PLY LOCATION
REPAIR PLY
LOCATIONS
0.50
TYPICAL
TAPER  TAPER
LENGTH  LENGTH
FOAMING
ADHESIVE
FILLERS
INBD
FIGURE 3: LEFT WING SKIN PANEL 521EB CHANGE
(SHEET 2 OF 4)
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### Page 31

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
as shown above.
Remove existing
plies, cut core and
install new plies in
accordance with (a).
Replace the five ex-
isting plies and add
one extra ply.
1521EBSkin PanelChange1
as shown.1-HoleLocate2
Drainage hole diam-
eter is 0.38 inch.
Clean and deburr
hole.
1-HoleDrill3
Diameter is 0.76
inch. Depth is 0.040
inch. Clean and de-
burr counterbore.
1-CounterboreDrill4
to the insert. Refer
to SOPM 20-43-03
as an accepted pro-
cedure.
--Chemical Conversion
Coating
Apply5
Apply one coat to
the insert. Refer to
SOPM 20-44-04 as
an accepted proce-
dure.
-BMS10-79, TYPE IIIPrimerApply
Bond insert into skin
panel. Refer to
SOPM 20-50-12,
Type 111 as an ac-
cepted procedure.
Type 94 is an accept-
able substitute.
169B12065-1INSERT, DRAIN HOLEInstall (New)6
to touch up finishes,
if necessary.
-BMS10-79, TYPE IIIPrimerApply7
-BMS10-60, TYPE II,
BAC707 GRAY GLOSS
EnamelApply
Rubber stamp part
number on the part.
Refer to SOPM 20-
50-10 as an accept-
ed procedure.
1SB 767-57-0121Part NumberApply8
FIGURE 3: LEFT WING SKIN PANEL 521EB CHANGE
(SHEET 3 OF 4)
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### Page 32

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) 767-200 SRM 51-70-08, 767-200SF SRM 51-70-08, 767-300 SRM 51-70-08, 767-300BCF SRM 51-70-
08, 767-300F SRM 51-70-08 or 767-400 SRM 51-70-08, as applicable.
FIGURE 3: LEFT WING SKIN PANEL 521EB CHANGE
(SHEET 4 OF 4)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
FWD
INBD
2.25
1.75
1.90
1.70  PANEL
B-
FWD
2.80
2.60  B-B
2.25
1.75  INSERT
D
INBD  1997891
A-A
FIGURE 4: RIGHT WING SKIN PANEL 621EB CHANGE
(SHEET 1 OF 4)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
TEDLAR
APPLICATION
EXTRA
REPAIR PLY
ADHESIVE
FILM
5 ORIGINAL
PLIES
EXTRA REPAIR
PLY LOCATION
REPAIR PLY
LOCATIONS
0.50
TYPICAL
TAPER  TAPER
LENGTH  LENGTH
FOAMING
ADHESIVE
FILLERS
INBD
1997892
FIGURE 4: RIGHT WING SKIN PANEL 621EB CHANGE
(SHEET 2 OF 4)
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### Page 35

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
as shown above.
Remove existing
plies, cut core and
install new plies in
accordance with (a).
Replace the five ex-
isting plies and add
one extra ply.
1621EBSkin PanelChange1
as shown.1-HoleLocate2
Drainage hole diam-
eter is 0.38 inch.
Clean and deburr
hole.
1-HoleDrill3
Diameter is 0.76
inch. Depth is 0.040
inch. Clean and de-
burr counterbore.
1-CounterboreDrill4
to the insert. Refer
to SOPM 20-43-03
as an accepted pro-
cedure.
--Chemical Conversion
Coating
Apply5
Apply one coat to
the insert. Refer to
SOPM 20-44-04 as
an accepted proce-
dure.
-BMS10-79, TYPE IIIPrimerApply
Bond insert into skin
panel. Refer to
SOPM 20-50-12,
Type 111 as an ac-
cepted procedure.
Type 94 is an accept-
able substitute.
169B12065-1INSERT, DRAIN HOLEInstall (New)6
to touch up finishes,
if necessary.
-BMS10-79, TYPE IIIPrimerApply7
-BMS10-60, TYPE II,
BAC707 GRAY GLOSS
EnamelApply
Rubber stamp part
number on the part.
Refer to SOPM 20-
50-10 as an accept-
ed procedure.
1SB 767-57-0121Part NumberApply8
FIGURE 4: RIGHT WING SKIN PANEL 621EB CHANGE
(SHEET 3 OF 4)
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### Page 36

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) 767-200 SRM 51-70-08, 767-200SF SRM 51-70-08, 767-300 SRM 51-70-08, 767-300BCF SRM 51-70-
08, 767-300F SRM 51-70-08 or 767-400 SRM 51-70-08, as applicable.
FIGURE 4: RIGHT WING SKIN PANEL 621EB CHANGE
(SHEET 4 OF 4)
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
WBL
97.95
STA
558
STA
798
STA
1106.6
WSTA
404.4
WSTA
1106.6
B
INBD
1996980
FIGURE 5: LEFT WING SEAL DOOR CHANGE AT OSS 424.097
(SHEET 1 OF 3)
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### Page 38

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
as shown.1114T2605-19DETAIL, TABLocate1
as shown.2-HoleLocate2
Final hole size is
0.159 - 0.167 inch.
Countersink is 100
degrees.
2-HoleDrill
FIGURE 5: LEFT WING SEAL DOOR CHANGE AT OSS 424.097
(SHEET 2 OF 3)
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### Page 39

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1114T2605-19DETAIL, TABRemove / Keep3
and deburr.2-HoleClean
Fay seal as shown.
Refer to SOPM 20-
50-19 as an accept-
ed procedure.
-BMS5-45SealantApply4
1114T2605-19DETAIL, TABInstall (New)5
2BACR15CE5AD4RIVETInstall (New)
Apply fillet seal
around tab. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
-BMS5-45SealantApply
Fill entire hole with
sealant. Refer to 767
AMM 51-31-01 or
767-400 AMM 51-
31-01, as applicable,
as an accepted pro-
cedure for aerody-
namic smoothness
information.
-BMS5-45SealantApply6
FIGURE 5: LEFT WING SEAL DOOR CHANGE AT OSS 424.097
(SHEET 3 OF 3)
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### Page 40 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
WBL
97.95
STA
558
STA
798
STA
1106.6
WSTA
404.4
WSTA
1106.6
B
INBD
1997897
FIGURE 6: RIGHT WING SEAL DOOR CHANGE AT OSS 424.097
(SHEET 1 OF 3)
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### Page 41

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
as shown.1114T2605-19DETAIL, TABLocate1
as shown.2-HoleLocate2
Final hole size is
0.159 - 0.167 inch.
Countersink is 100
degrees.
2-HoleDrill
FIGURE 6: RIGHT WING SEAL DOOR CHANGE AT OSS 424.097
(SHEET 2 OF 3)
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BOEING SERVICE BULLETIN 767-57-0121

### Page 42

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1114T2605-19DETAIL, TABRemove / Keep3
and deburr.2-HoleClean
Fay seal as shown.
Refer to SOPM 20-
50-19 as an accept-
ed procedure.
-BMS5-45SealantApply4
1114T2605-19DETAIL, TABInstall (New)5
2BACR15CE5AD4RIVETInstall (New)
Apply fillet seal
around tab. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
-BMS5-45SealantApply
Fill entire hole with
sealant. Refer to 767
AMM 51-31-01 or
767-400 AMM 51-
31-01, as applicable,
as an accepted pro-
cedure for aerody-
namic smoothness
information.
-BMS5-45SealantApply6
FIGURE 6: RIGHT WING SEAL DOOR CHANGE AT OSS 424.097
(SHEET 3 OF 3)
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### Page 43 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
WBL
97.95
STA
558
STA
798
STA
1106.6
WSTA
404
WSTA
1106
4X5
BEFORE  1997286
FIGURE 7: LEFT WING RIB CHANGE AT OSS 464.475
(SHEET 1 OF 4)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
• AFTER
A-A
WD
6) BOLT
NUT  6) WASHER
WASHER 6)
OUTER
PLUG
C-C
(10)
FWD
B-B
- 0.10 MAX  1997287
D-D
FIGURE 7: LEFT WING RIB CHANGE AT OSS 464.475
(SHEET 2 OF 4)
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### Page 45

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
2-GrommetRemove1
Use BMS11-7 Sol-
vent to clean surface
where grommet was
removed. Refer to
SOPM 20-30-03 as
an accepted proce-
dure.
2-HoleClean2
3-FastenerRemove3
1-Wire Support AssemblyRemove
if present.1-ShimRemove
if necessary. Hole
diameter is 0.190 -
0.193 inch.
3-HoleDrill / Ream4
and deburr, if neces-
sary.
3-HoleClean
wet with BMS5-45
sealant.
3BACB30VT6K5BOLTInstall (New)5
3BACC30BL6COLLARInstall (New)
1114T2605-17DETAIL, PLUG INNERInstall (New)6
Fay seal entire inner
surface with BMS5-
45 sealant prior to
installation. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
2114T2605-15DETAIL, PLUG OUTERInstall (New)
wet with BMS5-45
sealant. Refer to
SOPM 20-50-19,
Method 2 as an ac-
cepted procedure.
1BACB30NR4K7BOLTInstall (New)
Install under head of
BACB30NR4K7 bolt.
1BACW10BN4ACWASHERInstall (New)
Torque nut to 78 -
82 in-lbs.
1BACN10YR4CDNUTInstall (New)
Install under
BACN10YR4CD nut.
1NAS1149D0463JWASHERInstall (New)
FIGURE 7: LEFT WING RIB CHANGE AT OSS 464.475
(SHEET 3 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 07, 2010
767-57-0121
45 of 68
BOEING SERVICE BULLETIN 767-57-0121

### Page 46

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Apply fuel fillet seal
as shown. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
-BMS5-45SealantApply7
Install seal at its fur-
thest forward posi-
tion within the hole.
Refer to SOPM 20-
50-19 as an accept-
ed procedure.
1BACS45B4SEALInstall (New)8
Prepack sealant
continuously along
inner surface of hole
and surface of seal.
Make sure seal re-
mains located in its
furthest forward posi-
tion. Refer to SOPM
20-50-19 as an ac-
cepted procedure.
-BMS5-45SealantApply9
Trim seal ring as
necessary up to
0.100 inch to allow
installation.
3BACS11BD8SEAL, RINGInstall (New)10
1MS16624-2175RING, RETAINING,
EXT
Install (New)11
Apply fillet seal
around the edges of
seal rings, rib hole
and front spar. Refer
to SOPM 20-50-19
as an accepted pro-
cedure.
-BMS5-45SealantApply12
FIGURE 7: LEFT WING RIB CHANGE AT OSS 464.475
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 07, 2010
767-57-0121
46 of 68
BOEING SERVICE BULLETIN 767-57-0121

### Page 47 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
WBL
97.95
STA
558
STA
798
STA
1106.6
WSTA
404
WSTA
1106
345
WD
BEFORE  1997915
FIGURE 8: RIGHT WING RIB CHANGE AT OSS 464.475
(SHEET 1 OF 4)
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Copyright © Unpublished Work - See page 1 for details.  47 0f 68

### Page 48 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
C-
FWD
AFTER  A-A
BOLT (
WASHER  6) NUT
) WASHER
INNER
PLUG
OUTER
PLUG
C-C
FWD
B-B
0.10 MAX  1997920
D-D
FIGURE 8: RIGHT WING RIB CHANGE AT OSS 464.475
(SHEET 2 OF 4)
Original Issue: October 07, 2010
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Copyright © Unpublished Work - See page 1 for details.  48 of 68

### Page 49

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
2-GrommetRemove1
Use BMS11-7 Sol-
vent to clean surface
where grommet was
removed. Refer to
SOPM 20-30-03 as
an accepted proce-
dure.
2-HoleClean2
3-FastenerRemove3
1-Wire Support AssemblyRemove
if present.1-ShimRemove
if necessary. Hole
diameter is 0.190 -
0.193 inch.
3-HoleDrill / Ream4
and deburr, if neces-
sary.
3-HoleClean
wet with BMS5-45
sealant.
3BACB30VT6K5BOLTInstall (New)5
3BACC30BL6COLLARInstall (New)
1114T2605-17DETAIL, PLUG INNERInstall (New)6
Fay seal entire inner
surface with BMS5-
45 sealant prior to
installation. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
2114T2605-15DETAIL, PLUG OUTERInstall (New)
wet with BMS5-45
sealant. Refer to
SOPM 20-50-19,
Method 2 as an ac-
cepted procedure.
1BACB30NR4K7BOLTInstall (New)
Install under head of
BACB30NR4K7 bolt.
1BACW10BN4ACWASHERInstall (New)
Torque nut to 78 -
82 in-lbs.
1BACN10YR4CDNUTInstall (New)
Install under
BACN10YR4CD nut.
1NAS1149D0463JWASHERInstall (New)
FIGURE 8: RIGHT WING RIB CHANGE AT OSS 464.475
(SHEET 3 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 07, 2010
767-57-0121
49 of 68
BOEING SERVICE BULLETIN 767-57-0121

### Page 50

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Apply fuel fillet seal
as shown. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
-BMS5-45SealantApply7
Install seal at its fur-
thest forward posi-
tion within the hole.
Refer to SOPM 20-
50-19 as an accept-
ed procedure.
1BACS45B4SEALInstall (New)8
Prepack sealant
continuously along
inner surface of hole
and surface of seal.
Make sure seal re-
mains located in its
furthest forward posi-
tion. Refer to SOPM
20-50-19 as an ac-
cepted procedure.
-BMS5-45SealantApply9
Trim seal ring as
necessary up to
0.100 inch to allow
installation.
3BACS11BD8SEAL, RINGInstall (New)10
1MS16624-2175RING, RETAINING,
EXT
Install (New)11
Apply fillet seal
around the edges of
seal rings, rib hole
and front spar. Refer
to SOPM 20-50-19
as an accepted pro-
cedure.
-BMS5-45SealantApply12
FIGURE 8: RIGHT WING RIB CHANGE AT OSS 464.475
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 07, 2010
767-57-0121
50 of 68
BOEING SERVICE BULLETIN 767-57-0121

### Page 51 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
WBL
97.95
STA
558
STA
798
STA
1170
INBD
G
FORWARD PITCH  OSS  OSS  OSS  OSS  OSS  OSS
LOAD FITTING  408.63  421.84  429.99  441.59  456.97  464.47
H  B
￾ D
- E
OSS  OSS  oss
416.20  426.99  437.39  1997300
A-A
FIGURE 9: LEFT WING LEADING EDGE SEALING
(SHEET 1 OF 4)
Original Issue: October 07, 2010
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Copyright © Unpublished Work - See page 1 for details.  51 of 68

### Page 52 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
B-B  C-C  D-D
FWD  FWD
E-E  F-F  G-G
FWD
H-H  I-I  1997370
FIGURE 9: LEFT WING LEADING EDGE SEALING
(SHEET 2 OF 4)
Original Issue: October 07, 2010
767-57-0121
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### Page 53 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
FWD  FWD
J-J  K-K
FORWARD PITCH
LOAD FITTING
3.9
3.3
6.2
5.6
NBD
C  FWD  1997812
FIGURE 9: LEFT WING LEADING EDGE SEALING
(SHEET 3 OF 4)
Original Issue: October 07, 2010
767-57-0121
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Copyright © Unpublished Work - See page 1 for details.  53 of 68

### Page 54

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Fill corner gaps as
shown.
-BMS5-16Hole Filling CompoundApply1
to base of forward
pitch load fitting as
shown.
-BMS5-125 TYPE IIILeveling CompoundApply2
with BMS5-16 hole
filling compound.
--HoleFill3
Brush sealant over
the surface as
shown.
-BMS5-45SealantApply4
if blocked. Make
sure drain path is
not blocked.
--Drain PathClean5
if blocked. Make
sure drain path is
not blocked. Primary
drain path minimum
diameter is 0.375
inch or equivalent
area.
--Primary Drain PathClean6
FIGURE 9: LEFT WING LEADING EDGE SEALING
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 07, 2010
767-57-0121
54 of 68
BOEING SERVICE BULLETIN 767-57-0121

### Page 55 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
WBL
97.95
STA
798
STA
1170
INBD
OSS  OSS  OSS  E~  oss  G-  OSS  K—  FORWARD PITCH
464.47  456.97  441.59  429.99  421.84  408.63  LOAD FITTING
B -  ¡ C-  D*  K
K
D ￾
B -
OSS  OSS  OSS
437.39  426.99  416.20  1997931
A-A
FIGURE 10: RIGHT WING LEADING EDGE SEALING
(SHEET 1 OF 4)
Original Issue: October 07, 2010
BOEING PROPRIETARY -  1210-29-292
Copyright © Unpublished Work - See page 1 for details.  39109

### Page 56 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
FWD
B-B  C-C  D-D
FWD  -WD  FWD
E-E  F-F  G-G
a.C
FWD
H-H  1997939
FIGURE 10: RIGHT WING LEADING EDGE SEALING
(SHEET 2 OF 4)
Original Issue: October 07, 2010
767-57-0121
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  56 of 68

### Page 57 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
FWD  FWD
J-J  K-K
FORWARD PITCH
LOAD FITTING
3.9
3.3
5.8
5.2
/ 6.2
5.6
FWD  1997950
FIGURE 10: RIGHT WING LEADING EDGE SEALING
(SHEET 3 OF 4)
Original Issue: October 07, 2010
BOEING PROPRIETARY -  767-57-0121
Copyright © Unpublished Work - See page 1 for details.  57 of 68

### Page 58

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Fill corner gaps as
shown.
-BMS5-16Hole Filling CompoundApply1
to base of forward
pitch load fitting as
shown.
-BMS5-125 TYPE IIILeveling CompoundApply2
with BMS5-16 hole
filling compound.
--HoleFill3
Brush sealant over
the surface as
shown.
-BMS5-45SealantApply4
if blocked. Make
sure drain path is
not blocked.
--Drain PathClean5
if blocked. Make
sure drain path is
not blocked. Primary
drain path minimum
diameter is 0.375
inch or equivalent
area.
--Primary Drain PathClean6
FIGURE 10: RIGHT WING LEADING EDGE SEALING
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 07, 2010
767-57-0121
58 of 68
BOEING SERVICE BULLETIN 767-57-0121

### Page 59 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
WBL
97.95
STA
558
STA
798
STA
1106.6
WSTA
404
WSTA
1106
.25
3.75
_ A
1997829
FIGURE 11: LEFT WING RIB SEALING AT OSS 464.475
(SHEET 1 OF 5)
Original Issue: October 07, 2010
BOEING PROPRIETARY -  767-57-0121
Copyright © Unpublished Work - See page 1 for details.  59 of 68

### Page 60 (OCR)

BOEING SERVICE BULLETIN 767-57-0121
C
FWD
A-A
1997843
FIGURE 11: LEFT WING RIB SEALING AT OSS 464.475
(SHEET 2 OF 5)
Original Issue: October 07, 2010
767-57-0121
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  60 of 68

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